Hi Greystoke, here is a calculation for your blades. Last two columns are what you are after: blade setting and chord length (linearised for easy construction). Near the root shapes is not important, so just ignore that and make the root in any way you can.

For example, at radius of 990mm from the axis of rotations, the setting angle should be 6.5288 degrees, and the chord length 297.6mm. This is based on the NACA 4412 profile, so you would scale that profile at each station to get the specified chord (chord = distance from front-most to back-most point). The setting angle is the angle between the chord and the plane of rotation.

If you are after perfection at the cost of construction complexity, then you should use the previous two columns, the ideal figures.

Im a college student from Greece and i make a project about the blades of wind turbines. I try to calculate the chord line and angle beta of each station of naca4412.Does any know the formulas for the calculations?

1) Im not sure but i think that lift coefficient cl changes along the blade. I have read that a good choice of cl is 0.6 at the wing tip with a gradual increase to 1.3 at the wing root. Do you have to suggest something?

2) ?? is the tip speed ratio. In my calculations does it change?

3) I found some charts from NASA about cl,cd and angle of attack for Re=3.110.000. This number of Re is ok? or I should find charts for higher Re number?

finally I calculated the chord and angle ?. Thank you very much fro your time !! Also I have found this site http://www.worldofkrauss.com/foils/793has very usefull information for anyone who is interested to design a blade (but Im sure that no one is going to use equations and charts ) An other one is http://easyultralightdesign.com/airfoils/index.php

I had seen the Krauss website - its great. Thanks for the other link. Still, I haven't found a good source of all the airfoil data, across a range of Re numbers. If you ever find one, please let me know!